Some Effects of Reynolds and Mach Numbers on the Lift of an NACA 0012 Rectangular Wing in the NACA 19-Foot Pressure Tunnel
Abstract
A short investigation was made in the NACA 19-foot pressure tunnel to determine the aerodynamic characteristics of a rectangular wing model constructed to NACA 0012 airfoil sections. The tests were run with the air in the tunnel at two different pressures: atmospheric (14.7 lb/sq in. abs.) and 35 pounds per square inch absolute. The Reynolds number ranged from 1,070,000 to 5,250,000 for the tests at atmospheric pressure and from 1,960,000 to 8,240,000 for the tests at a pressure of 35 pounds per square inch absolute. The results indicate a marked compressibility effect on the lift coefficients, particularly the maximum lift coefficients, which increase up to a velocity of approximately 150 miles per hour (a Mach number of 0.19) and then decrease rapidly. The results also indicate that, in wind-tunnel testing to determine maximum lift coefficients, compressibility effects may be avoided by limiting the tunnel air-stream test velocity to about 125 miles per hour (a Mach number of 0.17).
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1943
- Accession Number
- ADA801517
Entities
People
- Thomas C. Muse
Organizations
- National Advisory Committee for Aeronautics